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Automatic docking control system for carrier rocket and drain connector

An automatic docking and control system technology, which is applied in transportation and packaging, space navigation equipment, space navigation ground equipment, etc., and can solve the problems of manual docking and other connection

Active Publication Date: 2017-10-24
BEIJING INST OF SPACE LAUNCH TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Solve the problems caused by the connection of my country's launch vehicles relying on manual docking

Method used

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  • Automatic docking control system for carrier rocket and drain connector
  • Automatic docking control system for carrier rocket and drain connector
  • Automatic docking control system for carrier rocket and drain connector

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Embodiment Construction

[0077] The basic concept of the present invention is: an automatic docking control system for a launch vehicle loading and unloading connector, including: a monitoring unit, a motion control unit, a servo controller, a force detection unit, a locking mechanism, a six-degree-of-freedom parallel mechanism, and a visual monitoring unit; The visual monitoring unit uses the camera to detect the position and attitude of the interface on the launch vehicle arrow; the force monitoring unit uses the force and torque sensor to detect the force and torque generated after docking; the locking mechanism completes the locking of the filling and releasing connector and the interface on the arrow ; The motion control unit uses the visual monitoring unit and the force detection unit to control the movement of the six-free parallel mechanism; the servo driver completes the driving of the motor. The invention realizes the automatic docking and locking of the filling and releasing connector and th...

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Abstract

Disclosed is an automatic docking control system for a carrier rocket and a drain connector. The automatic docking control system comprises a monitoring unit, a motion control unit, a servo drive, a force detection unit, a locking mechanism, a six-degree of freedom parallel mechanism and a visual monitoring unit; the visual monitoring unit is used for detecting on-rocket interface position and posture of the carrier rocket by the aid of a camera; the force detection unit is used for detecting force and moment generated from docking of force and a torque sensor; the locking mechanism is used for locking the drain connector and an on-rocket interface; the motion control unit is used for controlling motion of the six-degree of freedom parallel mechanism by the aid of the visual monitoring unit and the force detection unit; the servo drive is used for driving a motor. By the arrangement, the drain connector and the on-rocket interface are automatically docked and locked under the condition of not changing the rocket body, and motion of the on-rocket interface is followed; compared with an existing system with an artificial docking method, the automatic docking control system has the advantages of labor saving, and personnel safety is guaranteed.

Description

technical field [0001] The invention relates to an automatic docking control system for a launch vehicle filling and releasing connector, and belongs to the technical field of launch vehicle ground equipment filling. Background technique [0002] The gas and liquid interface equipment between the launch vehicle or missile and the ground equipment is generally called a connector. Before launch, the launch vehicle has been connected with the connector through the interface on the arrow to complete various tests of the launch vehicle. [0003] At present, the docking of the connectors of my country's launch vehicles and the interfaces on the arrows is all done manually, especially the propellant filling and draining connectors (referred to as "filling and draining connectors"), which are manually and directly operated by the operator. The connection between the connector and the rocket body interface, and the liquid propellant of the launch vehicle is flammable, explosive, vola...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G5/00
CPCB64G5/00
Inventor 郑国昆李道平王小军刘毅白文龙杨之江
Owner BEIJING INST OF SPACE LAUNCH TECH
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